Saab 340

Length. 19.73. 20.73. 18.53.

Height. 7.00 m. 6.00. 7.50.

Wingspan. 21.44m. 20.53m. 19.73m.

Distance between wheels of main landing gear. 6.71. 7.61. 8.61.

Two blank EFIS CRT ́s (EADI and EHSI) on the right hand pilot ́s side indicate. DPU failure. MPU failure. AHRS failure.

When go-around is selected, the EADIs display a fixed pitch command of: 6,4o noseup. 9,5o noseup. 8,2o noseup. 12o noseup.

The radio altimeter maximum altitude indication is: 2500 ft. 1000 ft. 3000 ft.

The cockpit voice recorder (cvr), continuously records the last ______minutes of cockpit communications and sound. 15’. 20’. 30’. 45.

A failure of the Air Data Computer (ADC) is indicated by which of the following?. OAT indication turns to red dashes on the EHSI. MFD goes blank. A red flag appears on the RH Pilot ́s Airspeed Indicator. Fault light on the pressurization panel appears.

In the event of 26v AC failure. VOR signal will be unusable. LOC signals will be unusable. ADF signal will be unusable. None of the above.

None of the above. All of the above. Flaps beyond 15° during take off. Trim not in the Green arc during take off. CL not at max position during take off.

Rudder limit. Both a & b. Rudder limiter mechanism fails to limit. Rudder limiter power loss.

If the ROLL disconnect handle is pulled in flight: Roll control can be maintained with the controllable aileron. Roll control is marginal. The pilot has control of both ailerons; the copilot has no control of either aileron.

The Left hot battery bus provides power to which of the following?. All of the above. L Fire T handle. L Fire extinguisher bottle. Cargo fire extinguisher bottles.

The emergency battery is charged from the. Left battery bus. Left avionic bus. Either essential bus.

The series/parallel relay is energized during a battery start to: Connect the batteries in series, supplying 48 volts. Ensure the two inverters are running in parallel during the start sequence. None of the above.

The “blue” EXT PWR AVAIL light indicates?. GPU power is connected and at least 4 volts are available. GPU power is connected and powering the electrical busses. The access door to the GPU receptacle is open.

The “white” EXT PWR ON light indicates?. GPU power is connected and powering the electrical busses. The access door to the GPU receptacle is open. None of the above.

When will the GPU automatically disconnect from the electrical distribution system?. When the voltage excedes 31 volts. Both. When the voltage is less tan 10 volts.

When will the batteries automatically disconnect from the battery bus?. When the voltage drops below 24 volts. When the temperature exceeds 71 °c. When the voltage exceeds 31 volts.

During an engine start with GPU powering the aircraft, bellow what voltage will the GPU disconnect from the system?. 7 volts. 24 volt. 10 volt.

The two generators that provide DC power are?. 400 amp 28 VDC. 800 amp 28 VDC. 400 amp 22 VDC.

The “wild” ac frecuency is used for. Ice protection. Bus tie connection. Pressurization.

All control and monitoring of the electrical system is performed from. Overhead panel. Central and pedestal panel. Glareshield panel.

With external power on, the generators: May remain connected. Must be manually turned off. Automatically disconnect.

Each main inverter produces: 26- and 115-VAC, 400-Hz power. 22- and 300-VAC, 400-Hz power. 30- and 220-VAC, 60-Hz power.

The stall warning system gives you several warning of an impending stall. They are: Shaker, clacker, stick pusher, push 1 & 2 lights. Shaker only. Shaker and clacker only.

If the PUSHER DISARM button is pressed, how can the system been reset?. On the ground by maintenance. In the air after a stall test is completed. On the ground after a complete reset of the electrical system.

Which of the following CWP lights is NOT inhibited by the takeoff inhibit mode?. CONFIG. RUDDER LIMIT. AVIONIC VENT.

During icing conditions, which vertical speed mode should be selected?. IAS only. VS or IAS. HDG.

The yaw damper: Can be engaged with or without the autopilot engaged. Cannot be engaged until the autopilot is engaged. Cannot be engaged with the autopilot engaged.

How is the fuel heated for engine use in cold weather operations?. By engine oil from the propeller gear box. By engine bleed air. By engine exhaust air.

The fuel test switch located on the overhead panel does which of the following?. Fuel flow & fuel quantity indicators. MAIN PUMP light. LOW FUEL light.

What is the maximumusable fuel quantity for both tanks?. . 5800 lbs. 5690 lbs. 3000 lbs.

What is the maximum fuel imbalance between the left and right hand fuel tanks?. 200 lbs. 300 lbs. 100 lbs.

FUEL LOW LEVELlight comes on when?. Fuel level reaches about 300 lbs in either tank. Fuel level reaches 600 lbs in either tank. Fuel level reaches 100 lbs in either tank.

The standby pump located in the hopper tank is in use during: All of the above. Engine start. Defueling if activated. Main pump fails.

The standby pump automatically activates when differential pressure across the engine driven pump is. 5 psi. 9 psi. 10 psi.

The blue “FUELING” light on the status panel means. Fueling swich on refueling panel is in “FUEL PANEL” position. The aircraft is being refueling. Fueling panel door is open.

During engine start, the engine is supplied with fuel by: A standby boost pump. Residual fuel in the fuel control unit. The engine-driven boost pump. Gravity.

The engine driven alternator provides power to which of the following?. All of the above. DECU. Ng indication. Ignition.

What is the compressor configuration of the CT7-9B gas generator section?. 5 axial and 1 centrifugal. 1 axial and 5 centrifugal. 4 axial and 2 centrifugal.

Which of the following areas of the engine are heated with compressor bleed air for ice protection. Variable inlet geometry guide vanes. Splitter lip (inlet particle separation device). Both a & b.

Which of the following areas of the engine are heated by scavenge oil? a. Variable inlet geometry guide vanes. Frame vanes. plitter lip (inlet particle separation device). None of the above.

What device operates the inlet guide vanes and the AI/SBV?. HMU. ECU. Ctot.

The ignition system is divided into. All the above. Np overspeed relight ignition. Continuos ignition and auto ignition. Start ignition.

The propeller constant-speed range is: 1150 rpm to 1396 rpm. 1196 rpm to 1350 rpm. 1040 rpm to 1200 rpm.

If the HMU torque motor is cutout because of a malfunction, fuel flow is primarily controlled by the. Position of the power lever. Bottoming governor. Condition lever.

If ng drops to or below_________, the sub-idle re-light protection system in decu will turn the ignition of. 62 %. 60%. 72%.

When a deceleration (62% ng or below) of the engine is detected, the auto-ignition is turned on, the light on the center status panel illuminates, and ignition stays on for: 5 seconds. 10 seconds. 30 seconds.

What will cause the HYD caption on the CWP to illuminate?. Pressure below 1850 psi in the main accumulator. Both a & b. Temperature above 116 °c in the reservoir.

The fluid quantity indicator on the main reservoir is: Mechanically operated. Pressure operated. Spring operated.

With the HYDR PUMP switch in AUTO, the main hydraulic pump is automatically activated when. Landing gear extension is selected. Nosewheel steering is activated. Landing gear retraction is selected. Any of the above.

What does the BLD AIR LEAK light on the overhead panel indicate?. There is a leak detected in the bleed air line. The bleed valve did not close after receiving a closed signal. The thermostat has failed in the cabin.

What does the RECIRC light on the overhead panel indicate?. The recirculation fan ́s below normal speed (under speed condition). The recirculation fan is on. The X valve is open.

Under normal conditions the hp bleed valve is positioned: Fully closed. Half open. Half closed.

An automatic mode of operation for the pressurization system is: Pressurization. Landing. All the above. Flight.

The outflow valves are controlled: Both. Manually. Pneumatically.

The indicators associated with the pressurization system display: All the above. Differential pressure. Cabin rated.

Under normal conditions the Low-pressure bleed valve is positioned: Fully open. Three-quarter close. Fully closed.

The manually controlled part of the pressurization system is completely: Pneumatic. Static. Electric.

What do the “blue” ENGINE ANTI ICE lights on the Flight Status Panel indicate?. The engine anti-ice switch is in the ON position. The AI/SBV valve failed to open. The engine anti-ice has failed.

What does the DEICE OV TEMP light on the overhead panel indicate?. The de-ice boot temperature is excessive. The windshield are overheating. A patch on the boot has fallen off.

What do the “blue” PROP DE-ICE lights on the Flight Status Panel indicates?. a. If they are illuminated, that the PROP DE-ICE is ON. If they are not illuminatedthat the PROP DE-ICE is OFF or FAILED. Both A&B.

The power requiered for windshield heat is supplied from the: Ac generators. Inverters. DC generators.

FI STOP blue light on the status panel comes on: In case of the failure of the stop to close after t/o when the gear is retracted. This is the normal indication when the aircraft is electrically powered on ground. In case of activation of the emergency override function before landing gear is extended.

Fire detections systems provide warnings of: Engine fire. Exhaust duct over temperature. Both.

Fuselage smoke detection sensors: Are located in the avionics area, the lavatory, and the cargo compartment. Utilize a pulsed light beam and photo sensor to detect the presence of smoke. All the above.

Pulling an illuminated ENG fire handle: Causes the MASTER WARNING light to extinguish. Arms both engine fire bottles circuits. Silences the fire bell. All of them.

A short circuit in the engine fire detection system: Illuminates the FIRE DET FAIL light. Produces a triple chime. Illuminates the MASTER WARNING light.

The second stage of extinguishing agent released into the cargo compartment: Is a regulated flow over a 20 minute time span to prevent reignition. Occurs only if the fire starts a second time. Occurs only if the CARGO FIRE EXTG switch is positioned to ON a second time.

The green monitor lights on the deicer boot control panel are illuminated: When the respective boot is pressurized. When the BOOT IND switch is in ON. When the BOOT IND switch is in ONand the respective boot is pressurized.

The parking brakes: Trap pressure in the brake lines between the a-skid valves and the brakes. Should not be set if accum. Pressure is less than 1.700 psi. Can be set only if the main hyd pump is operating.

Anti-skid is not available when ground speed is below. 20kt. 50kt. 60 kt.

The main and nose gear uplocks: Are hydraulically engaged at retraction. Can be disengaged hydraulically or pneumatically. Are mechanically engaged at retraction.

Which of the following is not considered an emergency exit?. Cargo door. Main entrance door. Crew hatch.

Which of the following lights are not connected to the L/R Hot Battery Bus?. Cabin emergency light. Cargo light. Dome light.

In case of a “dual generator failure”, which of the following lights will illuminate the flight instruments whit Main batteries power?. Flood light. L/R instrument light. Map reading lights.

The time delay for illumination of the cargo compartment and entrance area is. 5 min. 10 min. 3 min.

The navigation lights can be powered from: A ground power unit. All of the above. The engine generators. Airplane batteries.